CN203050895U - Igniter and ignition starting device of turbojet engine - Google Patents
Igniter and ignition starting device of turbojet engine Download PDFInfo
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- CN203050895U CN203050895U CN 201220721988 CN201220721988U CN203050895U CN 203050895 U CN203050895 U CN 203050895U CN 201220721988 CN201220721988 CN 201220721988 CN 201220721988 U CN201220721988 U CN 201220721988U CN 203050895 U CN203050895 U CN 203050895U
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- igniter
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Abstract
The utility model discloses an igniter which comprises a base (1), a ceramic ignition head (3) arranged on the base (1) and a power supply line (2) connected with the ceramic ignition head (3). When the igniter provided by the utility model works, power of the engine is first transported to the ceramic head to ignite through the power supply line, the ceramic ignition head connected with the power supply is heated rapidly to realize heat start, and meanwhile, the combustion chamber of the engine is heated, so that the combustion chamber is in a high temperature state. The oil pipe of the engine gasifies fuel oil and sprays the fuel oil to the combustion chamber. The high temperature combustion chamber ignites the gasified fuel oil to realize the ignition process of the engine. The process needs 10-20 seconds. Compared with conventional ignition mode, the igniter is more convenient. The utility model further discloses an ignition starting device of the turbojet engine with the igniter.
Description
Technical field
The utility model relates to the turbojet engine technical field, more particularly, relates to igniter and turbojet engine ignition trigger device.
Background technique
Turbojet engine is a kind of turbogenerator, and characteristics are to rely on gas flow fully to produce thrust, are typically used as the power of high-speed aircraft.The small sized turbine air breathing engine is to utilize gas compressor that air is gone from the suction port inspiration, be compressed in the firing chamber, oil nozzle is to the oil plant of firing chamber ejection atomizing then, ignition mechanism is lighted high-pressure air and mist of oil mixed gas, mixture combustion expands, and promotes the worm gear rotation, through behind the worm gear, from the jet acting of puff prot, reaction force promotes motor and aircraft flies forward.
Traditional small sized turbine air breathing engine ignition trigger device comprises igniter, oil pipe and tracheae three parts, igniter adopts the tungsten filament design usually, oil pipe and tracheae are respectively with in fuel oil and the air input firing chamber, indoor gasoline and the AIR MIXTURES of igniter energising back ignition combustion, make the gas mixture in the firing chamber burn, make the combustion gas that produces High Temperature High Pressure in the firing chamber thereby expand rapidly, realize the jet promotion function of motor.
Traditional ignition mechanism needs oil pipe and tracheae to be equipped with simultaneously, designing two portions has increased the load weight of motor, thereby the power capacity of waste part motor, and short, the poor stability of traditional tungsten filament igniting design service life, need regularly change, increase the maintenance cost of small sized turbine air breathing engine and used inconvenience.
Therefore, how to improve stability and working life, reduce maintenance rate and the maintenance expenses of motor, become the technical problem that those skilled in the art need to be resolved hurrily.
The model utility content
In view of this, the utility model provides a kind of igniter and turbojet engine ignition trigger device, to improve stability and working life, reduces maintenance rate and the maintenance expenses of motor.
For achieving the above object, the utility model provides following technological scheme:
A kind of igniter comprises:
Base;
Be arranged at the ceramic ignition head on the described base;
The power line that links to each other with described ceramic ignition head.
Preferably, in above-mentioned igniter, described ceramic ignition head is silicon nitride firing head.
Preferably, in above-mentioned igniter, described base is copper pedestal.
A kind of turbojet engine ignition trigger device comprises igniter and oil pipe, and described igniter is as above each described igniter.
From above-mentioned technological scheme as can be seen, the igniter that the utility model provides, when its work, at first by power line the electric power of motor is flowed to the ceramic ignition head, temperature raise rapidly after the ceramic ignition head was connected power supply, realize thermal starting, the heated engine firing chamber makes and is the condition of high temperature in the firing chamber simultaneously, the oil pipe of motor sprays into gasification of fuel oil in the firing chamber simultaneously, the fuel oil of gasification is lighted in the firing chamber of high temperature, realize the igniting process of motor, this process need 10-20 second, more traditional firing mode is faster.
Firing head of the present utility model adopts ceramic material, its quick heating and high temperature resistant, wear-resistant, not fragile when realizing the engine ignition effect, reduced the maintenance probability of motor, the more traditional tungsten filament ignition mechanism volume of ceramic ignition head is small and exquisite, has alleviated the load weight of motor.The ceramic ignition head life-span can reach 50,000 hours, is far longer than the working life of motor, so adopt the utility model in use to change, has reduced the maintenance user cost of motor.The utility model ceramic igniter only needs an oil pipe can realize ignition operation, because the ceramic ignition head of high temperature can raise the burning room temperature rapidly, the fuel oil of gasification can be lighted under hot environment, traditional tungsten filament firing head must just can be lighted by gas mixture, therefore need design oil pipe and tracheae, the utility model only needs an oil pipe to reduce the own wt of motor, can effectively improve the jet efficient of motor.Base of the present utility model is according to the volume design of ceramic ignition head, small volume and less weight can reduce the own wt of motor equally, and the utility model both can have been realized the ignition operation of motor, can reduce load weight and maintenance probability and the maintenance cost of motor again, have good using effect.
Description of drawings
The structural representation of the igniter that Fig. 1 provides for the utility model embodiment.
Embodiment
The utility model discloses a kind of igniter and turbojet engine ignition trigger device, to improve stability and working life, reduce maintenance rate and the maintenance expenses of motor.
Below in conjunction with the accompanying drawing among the utility model embodiment, the technological scheme among the utility model embodiment is clearly and completely described, obviously, described embodiment only is the utility model part embodiment, rather than whole embodiments.Based on the embodiment in the utility model, those of ordinary skills are not making the every other embodiment who obtains under the creative work prerequisite, all belong to the scope of the utility model protection.
See also Fig. 1, the structural representation of the igniter that Fig. 1 provides for the utility model embodiment.
The igniter that the utility model embodiment provides comprises base 1, ceramic ignition head 3 and power line 2.
Wherein, ceramic ignition head 3 is arranged on the described base 1, and power line 2 links to each other with described ceramic ignition head 3.
The igniter that the utility model provides, when its work, at first by power line the electric power of motor is flowed to the ceramic ignition head, temperature raise rapidly after the ceramic ignition head was connected power supply, realized thermal starting, the heated engine firing chamber makes and is the condition of high temperature in the firing chamber simultaneously, the oil pipe of motor sprays into gasification of fuel oil in the firing chamber simultaneously, and the fuel oil of gasification is lighted in the firing chamber of high temperature, realizes the igniting process of motor, this process need 10-20 second, more traditional firing mode is faster.
Firing head of the present utility model adopts ceramic material, its quick heating and high temperature resistant, wear-resistant, not fragile when realizing the engine ignition effect, reduced the maintenance probability of motor, the more traditional tungsten filament ignition mechanism volume of ceramic ignition head is small and exquisite, has alleviated the load weight of motor.The ceramic ignition head life-span can reach 50,000 hours, is far longer than the working life of motor, so adopt the utility model in use to change, has reduced the maintenance user cost of motor.
In the present embodiment, described ceramic ignition head 3 is silicon nitride firing head, also can be other ceramic material, and the utility model is not limited to silicon nitride.Described base 1 is copper pedestal, also can be other resistant to elevated temperatures material.
The utility model also provides a kind of turbojet engine ignition trigger device, comprises igniter and oil pipe, and wherein, described igniter is the as above disclosed igniter of embodiment.Because this turbojet engine ignition trigger device has adopted above-mentioned igniter, therefore have all technique effects of above-mentioned igniter concurrently, this paper does not repeat them here.
The utility model ceramic igniter only needs an oil pipe can realize ignition operation, because the ceramic ignition head of high temperature can raise the burning room temperature rapidly, the fuel oil of gasification can be lighted under hot environment, traditional tungsten filament firing head must just can be lighted by gas mixture, therefore need design oil pipe and tracheae, the utility model only needs an oil pipe to reduce the own wt of motor, can effectively improve the jet efficient of motor.Base of the present utility model is according to the volume design of ceramic ignition head, small volume and less weight can reduce the own wt of motor equally, and the utility model both can have been realized the ignition operation of motor, can reduce load weight and maintenance probability and the maintenance cost of motor again, have good using effect.
Each embodiment adopts the mode of going forward one by one to describe in this specification, and what each embodiment stressed is and other embodiments' difference that identical similar part is mutually referring to getting final product between each embodiment.
To the above-mentioned explanation of the disclosed embodiments, make related domain professional and technical personnel can realize or use the utility model.Multiple modification to these embodiments will be apparent concerning those skilled in the art, and defined General Principle can realize under the situation that does not break away from spirit or scope of the present utility model in other embodiments herein.Therefore, the utility model will can not be restricted to these embodiments shown in this article, but will meet the wideest scope consistent with principle disclosed herein and features of novelty.
Claims (4)
1. an igniter is characterized in that, comprising:
Base (1);
Be arranged at the ceramic ignition head (3) on the described base (1);
The power line (2) that links to each other with described ceramic ignition head (3).
2. igniter as claimed in claim 1 is characterized in that, described ceramic ignition head (3) is silicon nitride firing head.
3. igniter as claimed in claim 1 is characterized in that, described base (1) is copper pedestal.
4. a turbojet engine ignition trigger device comprises igniter and oil pipe, it is characterized in that, described igniter is as each described igniter of claim 1-3.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220721988 CN203050895U (en) | 2012-12-14 | 2012-12-14 | Igniter and ignition starting device of turbojet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220721988 CN203050895U (en) | 2012-12-14 | 2012-12-14 | Igniter and ignition starting device of turbojet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203050895U true CN203050895U (en) | 2013-07-10 |
Family
ID=48733854
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220721988 Expired - Fee Related CN203050895U (en) | 2012-12-14 | 2012-12-14 | Igniter and ignition starting device of turbojet engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203050895U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103452704A (en) * | 2013-08-09 | 2013-12-18 | 蔡肃民 | Miniature turbojet midair windmill ignition device |
| CN107762636A (en) * | 2017-10-23 | 2018-03-06 | 南京航空航天大学 | Kerosene igniter and ignition method applied to micro turbine engine starting system |
| CN108167080A (en) * | 2017-11-20 | 2018-06-15 | 北京动力机械研究所 | A kind of fanjet startup combustor structure |
-
2012
- 2012-12-14 CN CN 201220721988 patent/CN203050895U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103452704A (en) * | 2013-08-09 | 2013-12-18 | 蔡肃民 | Miniature turbojet midair windmill ignition device |
| CN107762636A (en) * | 2017-10-23 | 2018-03-06 | 南京航空航天大学 | Kerosene igniter and ignition method applied to micro turbine engine starting system |
| CN108167080A (en) * | 2017-11-20 | 2018-06-15 | 北京动力机械研究所 | A kind of fanjet startup combustor structure |
| CN108167080B (en) * | 2017-11-20 | 2019-05-10 | 北京动力机械研究所 | A kind of fanjet startup combustor structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130710 Termination date: 20151214 |
|
| EXPY | Termination of patent right or utility model |